[go: up one dir, main page]

EP2297431B1 - Verbindungselement mit demontagevorrichtung zur befestigung von statorelementen in einer turbomaschine - Google Patents

Verbindungselement mit demontagevorrichtung zur befestigung von statorelementen in einer turbomaschine Download PDF

Info

Publication number
EP2297431B1
EP2297431B1 EP09745775.8A EP09745775A EP2297431B1 EP 2297431 B1 EP2297431 B1 EP 2297431B1 EP 09745775 A EP09745775 A EP 09745775A EP 2297431 B1 EP2297431 B1 EP 2297431B1
Authority
EP
European Patent Office
Prior art keywords
locking unit
unit according
circumferential
passage
locking
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP09745775.8A
Other languages
English (en)
French (fr)
Other versions
EP2297431A1 (de
Inventor
Alain Dominique Gendraud
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2297431A1 publication Critical patent/EP2297431A1/de
Application granted granted Critical
Publication of EP2297431B1 publication Critical patent/EP2297431B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B2/00—Friction-grip releasable fastenings
    • F16B2/20—Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening
    • F16B2/22—Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening of resilient material, e.g. rubbery material
    • F16B2/24—Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening of resilient material, e.g. rubbery material of metal
    • F16B2/241—Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening of resilient material, e.g. rubbery material of metal of sheet metal
    • F16B2/245—Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening of resilient material, e.g. rubbery material of metal of sheet metal external, i.e. with contracting action
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the present invention relates generally to a locking member for a ring sector fixing device on an aircraft turbomachine casing, for example a turbine casing.
  • an organ is for example known from the document EP 0 967 364 .
  • the invention also relates to a turbomachine for an aircraft comprising such locking members, this turbomachine being able to take the form of a turboprop or a turbojet engine.
  • ring sectors circumferentially fixed on the housing around the turbine blades of a turbojet engine, these sectors jointly forming a continuous cylindrical envelope externally defining the passage of the gas passage in the turbine .
  • the ring sectors are mounted on an inner casing of the turbine by means of crankcase elements, called intermediate crankcase elements or spacers, on which they are hooked at their front end and held at their rear end by locking C-shaped or U-coated. These are engaged axially / longitudinally from the rear on circumferential flanges of the rear ends of the ring sectors and the intermediate housing members, to keep them radially pressed against each other.
  • This fixing ring sectors on the intermediate elements of the turbine housing allows them to follow the thermal expansion and contraction of the turbine housing, in which hot gases or cold gases are injected to control its thermal expansion and contraction in order to to keep a radial clearance as low as possible between the inner surfaces of the ring sectors and the ends of the blades of the turbine, and thus increase the efficiency of the turbine.
  • the locking members together form an annular locking device centered on the axis of the turbomachine, each member thus forming only an angular sector of this device.
  • Each member comprises two longitudinal clamping branches extending axially / longitudinally rearwards and connected at their rear ends by a connecting branch, while their front ends are intended to press between them at least one ring sector. against at least one crankcase element. These last two elements radially pressed against each other are actually provided to be housed in the space formed between the two longitudinal branches, open longitudinally forwards.
  • the locking members are designed, in particular with regard to the elasticity and spacing of the two longitudinal branches, for the applied radial clamping is effective.
  • the extraction of these locking members proves extremely difficult to achieve, because of the large radial clamping force exerted by the longitudinal branches. on the circumferential edges. Therefore, the extraction usually requires the use of tools by the operator, tooling generally having an unsuitable shape, likely to damage the locking members and the surrounding elements.
  • Such a situation occurs for example when using a screwdriver, the operator tries to slip between one of the longitudinal branches of the body and the circumferential edge in contact with this branch. Indeed, the screwdriver is then used as a lever arm, likely to damage both the longitudinal branch and the circumferential edge concerned, or to injure the operator.
  • the invention therefore aims to at least partially overcome the disadvantages mentioned above, relating to the achievements of the prior art.
  • the invention firstly relates to a locking member for a ring sector fixing device on an aircraft turbomachine casing, said member extending in a circumferential direction between a first circumferential end. and a second circumferential end, said member having, in section along a plane orthogonal to said circumferential direction, two clamping legs interconnected at their rear end by a connecting branch extending substantially parallel to a general spacing direction of two clamping legs, the front ends of the two clamping arms being intended to press between them at least one ring sector against at least one housing element.
  • said member is provided, on either side of a fictitious median plane orthogonal to said circumferential direction, with a passage allowing the gripping of said member, each passage being made in said connecting branch, in extending along a line substantially parallel to said spacing direction.
  • the member according to the invention provides in an original manner means for gripping, intended to facilitate its extraction after it has been set up on the ring sectors, for example using a suitable tool.
  • the particular positioning of the passages at the level of the connecting branch implies that they can easily cooperate with an extraction tool without risk of damaging the functionality of this locking member, particularly because of the lack of direct contact between the tool and the aforementioned front ends.
  • the fact of gripping these passages with a tool does not generate any direct mechanical stress on the front ends of the clamping legs which therefore can not be damaged by the pressure of the tool, the stresses being essentially concentrated on the connection branch offset towards the rear of the sensitive zone.
  • each guideline is a straight line, for example extending substantially radially, and therefore orthogonally to said circumferential direction along which the locking member extends.
  • each straight line preferably passes through an axis of a turbine equipped with a plurality of these members to ensure the plating of the ring sectors against crankcase elements.
  • the orientation of the guidelines of the passages could be different from the radial direction, as for example fixed so that the two guidelines are substantially parallel to each other.
  • the two passages are arranged on or near respectively said first circumferential end and said second circumferential end. These ends correspond to the portions of the organ that are least stressed when the latter is in the tightening condition of the ring sectors, so that the presence of the passages at these locations only creates a negligible mechanical weakening of the body. , requiring no oversizing of the surrounding areas.
  • each passage is substantially cylindrical, of axis corresponding to said guideline.
  • the access with the tool is authorized on both sides of the organ, according to the guideline, while in the second case, access is only allowed from the only side opens the blind passage.
  • each passage takes the form of a groove extending along the guideline, namely that the bottom of this groove extends substantially parallel to the spacing direction.
  • each groove is made to open in said circumferential direction.
  • each groove could be made to open backwards in one direction longitudinal extending substantially from each of the two clamping legs, without departing from the scope of the invention.
  • each groove has, in a view taken externally with respect to the member and according to said guideline, a substantially semicircular shape.
  • each groove forms at least one abutment surface on said connecting branch, said abutment surface being substantially oriented towards an inter-branch space of the member, defined between said clamping limbs.
  • This abutment surface can thus serve as a bearing surface for an extraction tool, which can then be biased in the longitudinal direction towards the rear to cause the desired extraction.
  • the abutment surface may have different shapes, for example a curve in the preferred case of the aforementioned semicircular shape of the groove, but the goal still remains to form with this surface a stop in the longitudinal direction towards the rear, for a tool requested in the latter direction after being introduced in the associated passage.
  • each passage has, in a view taken externally with respect to the member and according to said guideline, a closed delimitation line.
  • a closed delimitation line In this respect, it may be delimitation line generally oblong or in a circle, of the bore type.
  • the locking member forms an angular sector of an annular locking device intended to be centered on the axis of the turbine equipped with such a device.
  • the invention also relates to a ring sector fixing device on an aircraft turbomachine casing, comprising casing elements formed with first rear circumferential edges on which are applied second circumferential rear edges of the sectors of the aircraft.
  • the fastening device further comprising a plurality of locking members as described above, engaged on said first and second circumferential flanges to hold them pressed against each other.
  • the first and second circumferential rims extending rearward in the longitudinal direction, thus penetrate through the front opening of the members defined between the clamping limbs, in order to be kept radially plated thereon. against each other.
  • the invention also relates to an aircraft turbine engine turbine comprising a ring sector fixing device as described above, and / or at least one locking member as described above. It could alternatively be a turbomachine compressor, without departing from the scope of the invention.
  • the subject of the invention is an aircraft turbomachine comprising a turbine as described above, and / or a device for fixing ring sectors as described above, and / or at least one locking as described above, this turbomachine can indifferently be a turbojet or a turboprop.
  • a ring sector fixing device can be seen on an aircraft turbomachine turbine casing, according to a preferred embodiment of the present invention.
  • the direction A corresponds to the longitudinal direction or axial direction, parallel to the longitudinal axis 2 of the turbine and the turbomachine.
  • the direction B corresponds to the radial direction of the turbine, and the direction C to the circumferential direction.
  • the arrow 4 schematizes the main flow direction of the gas within the turbomachine, parallel to the direction A, the terms "before”, “upstream”, “back”, “downstream” used in the rest of the description being to be considered with respect to a direction of advancement of the aircraft under the action of the thrust of the turbomachine, this direction of advancement being contrary to the direction of the arrow 4.
  • reference numeral 10 designates the blades of a turbine engine high-pressure stage turbine, which rotate in a turbine casing 12 inside which are fixed housing elements 14, called spacers or intermediate elements crankcase .
  • the elements 14 carry ring sectors 16 arranged circumferentially around the axis of rotation 2 of the turbine, in the direction C, the internal surfaces of these ring sectors forming a continuous cylindrical surface which delimits externally a vein of passage of gas in the turbine.
  • the ring sectors 16 have an angular extent around the axis of the turbine, in the direction C, of about 10 to 20 °, and are for example thirty in number.
  • Each ring sector 16 comprises at its upstream end or forward end a circumferential edge 18 in a portion of a cylinder, through which it is hooked or fixed on a spacer 14, and also comprises at its rear end or downstream end a circumferential rim 20 in cylinder portion which is applied to a corresponding circumferential rim 22 in the cylinder portion of the spacer 14.
  • the circumferential flange 22 is said first circumferential flange
  • the circumferential flange 20 is said second circumferential flange.
  • the two circumferential flanges 20 and 22 extending in the direction A are held pressed against each other in the direction B in which they are superimposed, by a locking member 24 in the form of a C or U lying down which is engaged by the rear on the circumferential edges 20 and 22 and which keeps them tight radially on one another.
  • each member 24 forms an annular locking device centered on the axis 2, forming an integral part of the fixing device of the ring sectors.
  • each member 24 takes the form of an angular sector of the annular locking device, extending for example about 10 to 20 °, in the direction C.
  • they are provided adjacent in the direction C, for example the number of about thirty centered on the axis 2.
  • the ring sectors 16, the spacers 14 and the locking members 24 are made of metal, metal matrix composite (CMC), or other materials, and the locking members 24 are resiliently mounted tightly on the flanges. circumferential 20 and 22, to press them against each other with some prestress in the radial direction B, as will be detailed below.
  • CMC metal matrix composite
  • the second circumferential rim 20 of the ring sector 16 terminates at its rear end by radial teeth 26 facing outwards, and engaged in corresponding notches of the first circumferential rim 22 of the spacer 14, so as to immobilize each ring sector 16 rotating about the axis 2 of the turbine on a spacer 14.
  • each locking member 24 comprises, in section along a plane orthogonal to the direction C as is the case on the figure 2 , two clamping legs 28 and 30, said radially outer and radially inner longitudinal branches, respectively, which are connected rigidly to each other at their rear end by a connecting branch 32, and whose front ends are applied to the outer cylindrical face of the first circumferential flange 22 of the spacer 14 and on the inner cylindrical face of the second circumferential flange 20 of the ring sector 16, respectively.
  • the circumferential branches 28, 30 extend longitudinally in the direction A, and are spaced apart from one another in a general spacing direction, here preferably corresponding to the radial direction B.
  • the circumferential branch 32 s it extends substantially in this direction of spacing, namely in the radial direction B, to connect the two rear ends of the branches 28, 30. These two last branches together form an interbranch space 40 open forwards in the direction A for the passage of the flanges 20, 22, and closed rearwardly in this same direction A by the connecting branch 32.
  • the member 24 takes, in section orthogonal to the direction C, the shape of a C or a lying down, it should be understood that the member extends in this form on a given angular sector according to the direction C, between a first circumferential end 24a and a second circumferential end 24b, as shown in FIG. figure 3 .
  • one of the peculiarities of the present invention resides in the implantation, preferably at the circumferential ends 24a, 24b or in the vicinity thereof, of means making it possible to grip the locking member. 24, globally arranged towards the rear of the latter, in particular on the connecting branch 32.
  • These means take the form of two passages, each in the form of a groove, respectively provided on either side of the plane P2 constituting a fictitious median plane orthogonal to the direction C. More precisely and as mentioned above, the two grooves 42 are respectively arranged at the ends 24a, 24b, and have the particularity of extending each along a straight line 44, preferably arranged radially, parallel to the branch 32. As an indication, the two radial straight lines 44 being spaced circumferentially l one of the other, they are therefore not really parallel to each other, even if such a configuration remains possible.
  • each groove 42 extends cylindrically along its straight line 44, being at least partly formed on the connecting branch 32 that it passes preferably entirely in the direction B.
  • each groove 42 is made not only on the branch 32, but also through a rear portion of each of the two clamping legs 28, 30, while remaining at a distance from their front end plating. Nevertheless, each groove 42 could be made only on the branch 32, without departing from the scope of the invention.
  • Each groove 42 opens in the circumferential direction C, namely that its bottom 46 is oriented in this same direction, towards the outside of the body.
  • the groove 42 has a substantially semicircular shape, with the diameter corresponding to the opening of the groove, and the curved portion opposite the diameter corresponding to the bottom 46 thereof.
  • the curved portion adjacent to the diameter and located on the side of the branch 32, referenced 51, forms an abutment surface on this connecting branch, the abutment surface 51 therefore being substantially parallel to the radial direction B, and substantially oriented
  • This abutment surface 51 can then serve as a bearing surface for an extraction tool of the member 24, which can then be biased in the longitudinal direction towards the rear to cause the desired extraction.
  • the grooves 42 for gripping the member 24, are intended to facilitate its extraction after it has been put in place on the ring sectors 16.
  • the particular positioning of these means, deported backwards on the member 32, implies that they can easily cooperate with an extraction tool without the risk of damaging the functionality of this locking member 24, particularly because of the absence of direct contact between the tool and the front end of the legs 28, 30.
  • FIG. 6a and 6c it is schematized a method for extracting a locking member 24 initially located in its clamping position of the ring sectors 16, shown in the previous figures.
  • a tool 50 of appropriate shape is used, this tool generally having a fork-shaped head having two arms respectively provided with two ends 52, for example in the form of cylindrical pin shape substantially complementary to those of the grooves 42 in which they are intended respectively to penetrate, as is best seen on the figure 6b , seen in the radial direction B.
  • the two ends 52 are inserted respectively in the two grooves 42, for example by moving the tool in the radial direction, with the axis of each lug substantially coincident with the guide line of its associated groove.
  • the tool 50 can be presented above the member 24 in the direction B, or below it in the same direction, because of the character through the grooves.
  • the tool 50 is biased in the longitudinal direction A towards the rear, as shown in FIG. Figure 6c manually or automatically, which has the effect, if it is not already the case, of contact the lugs 52 with their respective abutment surfaces 51.
  • the continuation of this action on the tool 50 shown schematically by the arrow 54 on the Figure 6c , has the effect of gradually moving the member 24 in the direction A by sliding back the branches 28, 30 on the flanges 20, 22, until the total extraction of the member 24 releasing the sectors of ring 16 associated.
  • the figure 7 shows another extraction process for simultaneously producing the extraction of two directly consecutive members 24 in the direction C, using a single tool 50.
  • this tool 50 shown schematically on the figure 7 , also has a fork-shaped head having two arms respectively provided with two ends 52, for example in the form of cylindrical lug of a shape substantially complementary to those of the grooves 42 in which they are respectively intended to penetrate, namely preferably semicircular section.
  • the tool comprises a third lug 58 aligned in plan view with the two other lugs 52, and of complementary shape to that of the space formed by the two grooves 42 in look, in which he is destined to penetrate. This shape is then preferably of circular section.
  • the central lug 58 penetrates simultaneously into the two opposite grooves 42 belonging respectively to the two members 24, these two facing grooves forming, in effect, together a housing of substantially circular cross-section of complementary shape to that of the lug 58.
  • the two end lugs 52 are inserted respectively in the two other grooves 42 of the two members 24, namely those located at the circumferential ends of the doublet d concerned organs, always for example by moving the tool in the radial direction.
  • the tool 50 can be presented above the two members 24 in the direction B, or below it in the same direction.
  • the tool 50 is biased in the longitudinal direction A towards the rear, as shown by the arrow of the figure 7 .
  • each groove 42 takes a shape substantially circular non-closed, but extending over an angular sector greater than 180 °, to form two abutment surfaces 51 on either side of the opening of the groove.
  • Each of the two curved abutment surfaces 51 is therefore substantially parallel to the radial direction B, and substantially oriented towards the interspaced space 40.
  • these abutment surfaces 51 can then serve as a bearing surface for an extraction tool of the member 24, which can then be biased in the longitudinal direction towards the rear to cause the desired extraction.
  • the bottom of the groove 46 facing aft in the longitudinal direction A, can be indifferently provided on the connecting branch 32 all along the latter in the direction B, or on a rear portion of the clamping legs 28, 30, as shown in FIG. figure 8 .
  • each passage 42 has, in view (not shown) taken externally to the body and according to the guideline 44, a closed boundary line 60, for example of circular or oblong shape.
  • the passages made here are then also practiced only on the connecting branch 32, or straddling this branch 32 and the two clamping branches 28, 30, as has been shown on FIG. figure 9 .
  • each passage 42 which preferably extends all the way along the connecting branch in direction B, also forms an abutment surface 51 substantially parallel to this radial direction B, and substantially oriented towards the inter-branch space 40.
  • these abutment surfaces 51 can then serve as a bearing surface for an extraction tool of the member 24, which can then be biased in the longitudinal direction towards the rear to cause the desired extraction .

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Clamps And Clips (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (17)

  1. Verriegelungsorgan (24) für eine Vorrichtung zur Befestigung von Ringsektoren an einem Gehäuse einer Luftfahrzeugturbomaschine, wobei sich das Organ in einer Umfangsrichtung (C) zwischen einem ersten Umfangsende (24a) und einem zweiten Umfangsende (24b) erstreckt, wobei das Organ, im Schnitt entlang einer zu der Umfangsrichtung orthogonalen Ebene, zwei Klemmschenkel (28, 30) umfasst, die an ihrem hinteren Ende durch einen Verbindungsschenkel (32), welcher sich im Wesentlichen parallel zu einer Abstandshauptrichtung der beiden Klemmschenkel erstreckt, untereinander verbunden sind, wobei die vorderen Enden der beiden Klemmschenkel dazu bestimmt sind, zwischen diesen wenigstens einen Ringsektor gegen wenigstens ein Gehäuseelement zu drücken,
    dadurch gekennzeichnet, dass das Organ auf beiden Seiten einer fiktiven Mittelebene (P2), die zu der Umfangsrichtung orthogonal ist, mit einem Durchgang (42), der das Greifen des Organs ermöglicht, versehen ist, wobei jeder Durchgang in dem Verbindungsschenkel (32) ausgebildet ist und sich dabei entlang einer zu der Abstandsrichtung im Wesentlichen parallelen Leitlinie (44) erstreckt.
  2. Verriegelungsorgan nach Anspruch 1, dadurch gekennzeichnet, dass jede Leitlinie (44) eine gerade Linie ist.
  3. Verriegelungsorgan nach Anspruch 1 oder Anspruch 2, dadurch gekennzeichnet, dass die beiden Durchgänge (42) an dem oder in der Nähe des ersten Umfangsendes (24a) bzw. des zweiten Umfangsendes (24b) angeordnet sind.
  4. Verriegelungsorgan nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass jeder Durchgang (42) im Wesentlichen zylindrisch ist, mit einer Achse, die der Leitlinie (44) entspricht.
  5. Verriegelungsorgan nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass jeder Durchgang (42) durchgehend oder blind ausgebildet ist.
  6. Verriegelungsorgan nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass jede Leitlinie (44) im Wesentlichen radial verläuft.
  7. Verriegelungsorgan nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass jeder Durchgang (42) die Form einer sich entlang der Leitlinie erstreckenden Nut annimmt.
  8. Verriegelungsorgan nach Anspruch 7, dadurch gekennzeichnet, dass jede Nut (42) derart ausgebildet ist, dass sie sich in der Umfangsrichtung (C) öffnet.
  9. Verriegelungsorgan nach Anspruch 8, dadurch gekennzeichnet, dass jede Nut (42), in einer in Bezug auf das Organ äußeren Ansicht und entlang der Leitlinie (44), im Wesentlichen halbkreisförmig ist.
  10. Verriegelungsorgan nach einem der Ansprüche 7 bis 9, dadurch gekennzeichnet, dass jede Nut (42) wenigstens eine Anschlagfläche (51) an dem Verbindungsschenkel (32) bildet, wobei die Anschlagfläche im Wesentlichen zu einem Zwischenschenkelraum (40) des Organs, der zwischen den Klemmschenkeln (28, 30) definiert ist, gerichtet ist.
  11. Verriegelungsorgan nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass jeder Durchgang (42), in einer in Bezug auf das Organ äußeren Ansicht und entlang der Leitlinie (44), eine geschlossene Begrenzungslinie (60) aufweist.
  12. Verriegelungsorgan nach Anspruch 11, dadurch gekennzeichnet, dass jede Begrenzungslinie (60) eine insgesamt längliche Form oder Kreisform aufweist.
  13. Verriegelungsorgan nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass es einen Winkelsektor einer ringförmigen Verriegelungsvorrichtung bildet.
  14. Vorrichtung zur Befestigung von Ringsektoren an einem Gehäuse einer Luftfahrzeugturbomaschine, umfassend Gehäuseelemente (14), die mit ersten hinteren Umfangsrändern (22) gebildet sind, an die zweite hintere Umfangsränder (20) der Ringsektoren (16) angelegt sind, dadurch gekennzeichnet, dass die Befestigungsvorrichtung ferner eine Vielzahl von Verriegelungsorganen (24) nach einem der vorhergehenden Ansprüche umfasst, die auf die ersten und zweiten Umfangsränder (22, 20) gesteckt sind, um sie gegeneinander gedrückt zu halten.
  15. Turbine einer Luftfahrzeugturbomaschine, die eine Vorrichtung zur Befestigung von Ringsektoren nach Anspruch 14 und/oder wenigstens ein Verriegelungsorgan nach einem der Ansprüche 1 bis 13 umfasst.
  16. Luftfahrzeugturbomaschine, die eine Turbine nach Anspruch 15 und/oder eine Vorrichtung zur Befestigung von Ringsektoren nach Anspruch 14 und/oder wenigstens ein Verriegelungsorgan nach einem der Ansprüche 1 bis 13 umfasst.
  17. Turbomaschine nach Anspruch 16, dadurch gekennzeichnet, dass sie ein Turbostrahltriebwerk oder ein Turboprop-Triebwerk ist.
EP09745775.8A 2008-05-16 2009-05-14 Verbindungselement mit demontagevorrichtung zur befestigung von statorelementen in einer turbomaschine Active EP2297431B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0853182A FR2931196B1 (fr) 2008-05-16 2008-05-16 Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des passages radiaux permettant sa prehension
PCT/EP2009/055811 WO2009138443A1 (fr) 2008-05-16 2009-05-14 Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des passages radiaux permettant sa prehension

Publications (2)

Publication Number Publication Date
EP2297431A1 EP2297431A1 (de) 2011-03-23
EP2297431B1 true EP2297431B1 (de) 2016-06-15

Family

ID=39963086

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09745775.8A Active EP2297431B1 (de) 2008-05-16 2009-05-14 Verbindungselement mit demontagevorrichtung zur befestigung von statorelementen in einer turbomaschine

Country Status (9)

Country Link
US (1) US8721277B2 (de)
EP (1) EP2297431B1 (de)
JP (1) JP5443476B2 (de)
CN (1) CN102027199B (de)
BR (1) BRPI0912018B1 (de)
CA (1) CA2724256C (de)
FR (1) FR2931196B1 (de)
RU (1) RU2498088C2 (de)
WO (1) WO2009138443A1 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2931197B1 (fr) * 2008-05-16 2010-06-18 Snecma Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des passages axiaux pour sa prehension
FR2973069B1 (fr) * 2011-03-24 2014-09-12 Snecma Anneau de carter de stator de turbomachine
FR3009739B1 (fr) * 2013-08-13 2015-09-11 Snecma Amelioration pour le verrouillage de pieces de support d'aubage
FR3009740B1 (fr) 2013-08-13 2017-12-15 Snecma Amelioration pour le verrouillage de pieces de support d'aubage
ES2935815T3 (es) * 2013-09-06 2023-03-10 MTU Aero Engines AG (Des)montaje de un rotor de una turbina de gas, en particular delantero
US10100659B2 (en) * 2014-12-16 2018-10-16 Rolls-Royce North American Technologies Inc. Hanger system for a turbine engine component
US9932901B2 (en) * 2015-05-11 2018-04-03 General Electric Company Shroud retention system with retention springs
CN109641670B (zh) * 2016-06-06 2022-05-31 加拿大空客有限合伙公司 用于提升机的调节机构
DE102017104981B4 (de) * 2017-03-09 2021-01-28 Schaeffler Technologies AG & Co. KG Befestigungsmittel eines Aktuators einer Nockenwellenverstellvorrichtung
FR3105996B1 (fr) 2020-01-08 2021-11-26 Safran Aircraft Engines Organe de verrouillage destiné à l’assemblage d’une première pièce et d’une seconde pièce d’une turbomachine

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1139295A (en) * 1965-07-17 1969-01-08 Colt Ventilation & Heating Ltd Improvements in or relating to fastenings
US5197853A (en) * 1991-08-28 1993-03-30 General Electric Company Airtight shroud support rail and method for assembling in turbine engine
US5669757A (en) * 1995-11-30 1997-09-23 General Electric Company Turbine nozzle retainer assembly
US5970716A (en) * 1997-10-02 1999-10-26 General Electric Company Apparatus for retaining centerbody between adjacent domes of multiple annular combustor employing interference and clamping fits
FR2780443B1 (fr) * 1998-06-25 2000-08-04 Snecma Anneau de stator de turbine haute pression d'une turbomachine
US6233822B1 (en) * 1998-12-22 2001-05-22 General Electric Company Repair of high pressure turbine shrouds
US6435820B1 (en) * 1999-08-25 2002-08-20 General Electric Company Shroud assembly having C-clip retainer
US6412149B1 (en) * 1999-08-25 2002-07-02 General Electric Company C-clip for shroud assembly
FR2800797B1 (fr) * 1999-11-10 2001-12-07 Snecma Assemblage d'un anneau bordant une turbine a la structure de turbine
FR2815668B1 (fr) * 2000-10-19 2003-01-10 Snecma Moteurs Agencement de liaison d'un anneau de stator de turbine a une entretoise de support
CN100416045C (zh) * 2001-07-03 2008-09-03 Abb涡轮系统有限公司 用于轴流式涡轮机的工作叶片的锁定装置及锁定圆盘
FR2852053B1 (fr) * 2003-03-06 2007-12-28 Snecma Moteurs Turbine haute pression pour turbomachine
FR2887920B1 (fr) * 2005-06-29 2010-09-10 Snecma Dispositif de fixation de secteurs d'anneau sur un carter de turbine
FR2921410B1 (fr) * 2007-09-24 2010-03-12 Snecma Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des moyens permettant sa prehension
FR2922589B1 (fr) * 2007-10-22 2009-12-04 Snecma Controle du jeu en sommet d'aubes dans une turbine haute-pression de turbomachine
FR2923527B1 (fr) * 2007-11-13 2013-12-27 Snecma Etage de turbine ou de compresseur, en particulier de turbomachine

Also Published As

Publication number Publication date
CN102027199B (zh) 2013-08-28
FR2931196A1 (fr) 2009-11-20
EP2297431A1 (de) 2011-03-23
RU2010151721A (ru) 2012-06-27
BRPI0912018B1 (pt) 2019-11-26
JP5443476B2 (ja) 2014-03-19
JP2011521143A (ja) 2011-07-21
CN102027199A (zh) 2011-04-20
US8721277B2 (en) 2014-05-13
WO2009138443A1 (fr) 2009-11-19
RU2498088C2 (ru) 2013-11-10
CA2724256A1 (fr) 2009-11-19
CA2724256C (fr) 2016-08-30
BRPI0912018A2 (pt) 2015-10-06
FR2931196B1 (fr) 2010-06-18
US20110121150A1 (en) 2011-05-26

Similar Documents

Publication Publication Date Title
EP2297431B1 (de) Verbindungselement mit demontagevorrichtung zur befestigung von statorelementen in einer turbomaschine
WO2009138444A1 (fr) Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des passages axiaux pour sa prehension
EP2039885B1 (de) Verriegelungsorgan von Ringsektoren an einem Turbinengehäuse, das Greifmitteln umfasst
EP2425100B1 (de) Schaufelhaltevorrichtung für ein gebläse mit einem elastomer
EP2366060B1 (de) Gebläse für ein Turbotriebwerk mit einem Auswuchtsystem mit Blindlöchern zur Unterbringung von Gewichten und zugehöriges Turbotriebwerk
CA2557765C (fr) Dispositif d'immobilisation d'un anneau de retention axiale d'une aube, disque de rotor et anneau de retention associes, et rotor et moteur d'aeronef les comportant
FR2918722A1 (fr) Systeme de serrage a declenchement automatique pour un collier de serrage elastique.
FR2943985A1 (fr) Helice pour turbomachine d'aeronef comprenant un anneau de retention d'aubes monte autour du moyeu.
WO2014096647A1 (fr) Extension de carter intermediaire a conception amelioree
EP2705256B1 (de) Turbomaschinenrotor mit mittel zur axialbefestigung der schaufeln
FR3050719A1 (fr) Helice pour turbomachine d'aeronef comprenant des moyens de secours de calage en incidence de pale
FR2918409A1 (fr) Partie tournante de turbomachine comprenant des secteurs inter-aubes formant plateforme rapportes fixement sur un disque
FR2943984A1 (fr) Helice pour turbomachine d'aeronef comprenant un moyeu support d'aubes scinde en deux portions annulaires montees l'une sur l'autre.
FR2905139A1 (fr) Aube de rotor d'une turbomachine
FR2968363A1 (fr) Rotor de turbomachine avec une cale anti-usure entre un disque et un anneau
WO2011069940A1 (fr) Ensemble d'un jonc de retenue et d'un flasque de maintien dudit jonc
FR2887920A1 (fr) Dispositif de fixation de secteurs d'anneau sur un carter de turbine
FR2900979A1 (fr) Ensemble moteur pour aeronef comprenant un cone d'ejection des gaz monte sur un carter moteur a l'aide d'une bride de jonction externe
EP1807648B1 (de) Segmentierter klemmring und entsprechende anordnung und befestigungsverfahren
EP1855011B1 (de) Anordnung für den Verdichter eines Luftschiffmotors mit Schaufelrädern, befestigtem Hammer und geneigtem Fuss
FR2928714A1 (fr) Dispositif de raccordement pour transfert de fluide,circuit l'incorporant et son procede de montage/demontage.
EP3857028B1 (de) Verbesserte tubinenleitschaufel
FR2931195A1 (fr) Organe dissymetrique de verrouillage de secteurs d'anneau sur un carter de turbomachine
FR3040191A1 (fr) Helice pour turbomachine d'aeronef comprenant des moyens ameliores de retention radiale de pale d'helice

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20101112

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA RS

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160107

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 806624

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602009039244

Country of ref document: DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20160615

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160915

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 806624

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160615

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160916

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161015

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161017

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602009039244

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20170316

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170531

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170717

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170531

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170514

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170514

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20090514

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160615

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160615

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240419

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240418

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20240418

Year of fee payment: 16

Ref country code: FR

Payment date: 20240418

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20240418

Year of fee payment: 16